Abstract: A foam saddle is disclosed, where the foam saddle comprises a first casing, a second casing, a foam body and an intensified structure. The second casing is capped on the first casing. The foam body is formed in a cavity of the first casing and is bound to the first casing and the second casing. The intensified structure is embedded in the foam body. By means of the above structure, the first casing of the foam saddle of this invention and the foam body possess great bonding in between, and the foam body and the intensified structure possess great bonding in between too.

Abstract: An interchangeable colored bicycle has a bicycle framework with a main bicycle frame component part, a handlebar stem component part, and a wheel fork component part. Clear transparent tube members enclose and circumscribe these component parts. Free-flowing, colored liquids fill the interior spaces between the tube members and the component parts. The colored liquids in each interior space are different, thus allowing the bicycle to assume multiple colors. The free-flowing liquids can be drained from the tube members and different colored liquids can be poured into the interior spaces to change the colors of the bicycle.

Abstract: The present invention provides a bicycle comprising front and rear wheels and a frame including a main frame having a head tube and a top tube secured to the head tube at an intersection spaced from an upper end of the head tube. The intersection has a first lateral width, and the head tube above the intersection includes a tapered portion that tapers to a second lateral width narrower than the first lateral width. For example, the first lateral width can be at least three percent wider than the second lateral width. In one embodiment, the head tube above the tapered portion includes a flared portion that flares to a third lateral width wider (e.g., at least ten percent wider) than the second lateral width. In addition, the tapered portion can include a length that is larger (e.g., at least one hundred percent larger) than the second lateral width.

Abstract: A compression ring that is configured to be disposed between a bearing and a stem of a bicycle head parts assembly. The compression ring includes a central opening for receiving a steering column, a cut out portion, a first cable passing part disposed radially outwardly from the central opening, and a first positioning part for positioning the compression ring with respect to the stem so that the first cable passing part is aligned with a second cable passing part defined in the stem.

Abstract: The vehicle includes a frame member to be suspended relative to the ground. The suspension of the invention includes an arm (such as a swingarm), a slide link, and a control link. The arm having a first end and a second end; it extends between the frame generally at the first end and the ground-engaging member generally at the second end. The slide link is coupled between the frame and the arm. The slide link is rotationally fixed to the arm to rotationally move therewith. It is pivotally secured to the frame. The control link is also coupled to the frame and to the arm.

Abstract: A game cart bicycle attachment device is provided that is configured to secure the handle end of a wheeled game cart to the seat post of a bicycle. The device comprises an elongated and angled member that attaches at a first end to the bicycle seat post and at a second end to a game cart. The second end comprises a T-shaped connection, whereby a lateral attachment bar attaches to opposing sides of the game cart and the angled member connects at a third location. The angled member includes a telescoping structure to offset the game cart, while furthermore the lateral attachment bar is telescopically adjustable to accommodate different game cart sizes. The ends of the lateral attachment bar include U-shaped clevises, while a third clevis is adjustably disposed along the angled member. The device therefore attaches to the game cart at three distinct locations along its U-shaped handle.

Abstract: A brake lever reach adjustment includes a bracket, a brake lever and a reach adjusting assembly. The bracket to be mounted to a handlebar has a cavity therein. The brake lever is pivotally connected to the bracket, and defines two opposite wings. The reach adjusting assembly is disposed in the cavity of the bracket. The reach adjusting assembly has a lead screw and a movable block mounted about the lead screw. Specifically, the movable block selectively supports one of the two wings or is positioned between the two wings to adjust a position of the brake lever relative to the handlebar.

Abstract: This invention is directed to a variable speed drive system comprising: a frame having front and rear wheels; reciprocating pedals rotatably attached to the frame for supporting the rider; a pedal cam attached to one of the pedals at a hub where a distance between the hub and a first sprocket of the pedal cam is less than a distance between the hub and a second sprocket of the pedal cam; a coupling cam attached at a front axle and operably connected to the pedal cam so that when the pedal cam rotates when force is exerted downward on the pedal, the coupling cam rotates in an opposite direction from the pedal cam; and a drive sprocket carried by the coupling cam and linked to a wheel sprocket by a drive chain so that when the coupling cam rotates, the drive sprocket rotates causing the rear wheel to rotate.

Abstract: An apparatus for supporting an operator's foot riding a straddle-type vehicle. The apparatus includes a foot peg having a first portion connected to the vehicle and arranged for engaging a forward portion of the operator's foot adjacent to or including the ball of the foot. The apparatus also includes a second portion extending rearwardly of the first portion and arranged for engaging a rearward portion of the operator's foot adjacent to or including the heel during flexion of an ankle of the operator.

Abstract: The invention relates to an electric drive for bicycles, comprising two symmetrically arranged external-rotor type counter-rotating motors which are fed via two separate motor actuators/regulators that obtain the same control signal for power regulation purposes. The motors are mounted in an oscillating manner about an axis which is parallel, in particular substantially parallel, to the motor axis but offset with respect to the motor axis in a lateral manner, in particular in a parallel manner.

Abstract: A hull for a planing type watercraft has a front lift surface, a high lift surface, and a back planing surface. The high lift surface is adjacent a rockered keel area and between the front lift surface and the back planing surface. The center of dynamic lift on the high lift surface is at or in front of a point which is 15% of the hull length behind a total center of gravity of the hull under loading. At least the back one third of the high lift surface is cambered, and a beam of the high lift surface is greater than two thirds of the maximum width of the hull. The average camber of the front lift surface, the high lift surface, and the back planing surface together is less than or equal to zero.

Abstract: A wakesurfing boat for creating a wave suitable for surfing in the wake of the boat. A length to beam (L/B) ratio of 3.21 combined with a rounded hull bottom proximate the transom minimizes losses in the wake wave. Elliptical arcuate portions extending from starboard and port points on the transom to selected positions on the respective starboard and port bulwarks further minimize losses in the wake wave. The hull bottom defines an M-shaped portion and a V-shaped portion. A propulsion system includes an exhaust pipe projecting from the hull bottom below the waterline, with an exhaust opening forward of the transom. A propeller has a hub and at least three blades. A blade area, defined by a sum of the area of the blades, is larger than 70% of a disk area, defined by a sum of the hub and the blades.

Abstract: A rail system (40, 40?) of a ship (30) for positioning and arresting a hose (28) for supplying fluid material to an oil rig (10) from the ship (30) or supplying fluid material to the ship (30) from the oil rig (10). The rail system (40, 40?) comprises a rail (44, 44?, 46, 46?, 47) extending lengthwise at the upper edge of the bulwark of the ship (30). A vertical notch (48, 50) is provided in the rail having a bottom width corresponding to the diameter of the hose (28), and a locking element (52, 52?) of an elongated configuration being pivotally journaled adjacent to the vertical notch and being shiftable between a vertical position in which the hose (28) may be freely introduced into and positioned in the vertical notch (48, 50) and a horizontal position in which the locking element is blocking the entry into the notch and rests on the hose (28) for arresting the hose in the notch.

Abstract: A floating buoy for use in securing a looped wire assembly in marine environments is disclosed. The anchor buoy may include a buoyant body and a first opening and a second opening formed in the buoyant body, the first and second openings forming a passage through the buoyant body. The floating buoy may also include a loop-securing structure detachably connected to the buoyant body adjacent to the first opening, the loop-securing structure movable from a first position to a second position and vice versa, the loop-securing structure configured to cover the first opening such that the loop-securing structure in the first position defines a third opening that is narrower than both of the first opening and the second opening.

Abstract: Disclosed adjustable seat systems that provide a self-contained height-adjustable seat system for sit-on-top kayaking that allows the seat to be adjusted into various height and angle positions, while maintaining independent adjustment to the fore/aft position of the seat in the kayak. Some of the adjustable seat systems include a seat upper that includes a seat bottom and a seat back; a seat base adapted to slidably engage a flat surface in the watercraft; and at least two pivot mechanisms coupling the seat upper to the seat base, wherein the at least two pivot mechanisms allow the seat upper to be raised and lowered relative to the seat base. Some of the adjustable seat systems further include a front seat axis, a rear seat axis, a front base axis, and a rear base axis, a front pivot mechanism that pivotally engages both the front seat axis and the front base axis, and a rear pivot mechanism that pivotally engages both the rear seat axis and the rear base axis.

Abstract: A system of floating canal sections that connect end-to-end along a route to form a shipping canal and contain brine to prevent freezing. The canal sections of the present invention resemble floating dry-docks that are filled with the brine solution rather than with normal sea water. Sections can be floated into place and connected. Sections can be anchored to the sea floor. A typical section can be around 1000 feet long, 150 feet wide and about 50 feet deep. The sections can be manufactured anywhere and towed to the Arctic and connected. The use of brine prevents pollution if there should be a leak.

Abstract: To keep the water around an off-shore installation (1) free from a harmful impact of ice, a vessel (5) is used to deploy an anchor (6) in a position at a distance from the off-shore installation (1) and in a direction which, seen from the off-shore installation (1), is substantially in parallel with the direction of movement (P) of the ice. By means of the machinery of the vessel, which preferably comprises azimuth propellers, the direction of the anchor line is adjusted and so is the orientation of the vessel relative to the anchor line to the effect that the propellers can be used to crush and dispose of the ice without using energy to hold the vessel up against the pressure of the ice.

Abstract: Described herein is a more ergonomic, more stable kayak design including parallel port and starboard keels protruding from a hull of the kayak, the keels are sized and positioned such that a paddler can rest a heel and/or foot in each keel at a lower elevation than the paddler's hips, the dual keels providing two-point contact with the ground.

Abstract: A fin assembly includes a fin, a mounting base and a socket base. The mounting base is provided for permanent inclusion within a watercraft. The mounting base defines a cavity that is adapted for receiving the socket base. The socket base further includes a cavity adapted for receiving the fin. The socket base is further adapted for receiving an accessory.

Abstract: An embodiment of an apparatus includes a transducer array and a controller that is operable to cause the transducer array to generate a signal having a frequency, and to direct the signal toward an object having a resonant frequency that is approximately equal to the frequency of the signal. For example, an embodiment of a mine-hunting-and-neutralizing apparatus may generate an acoustic wave with a transducer array, and may disable or destroy a mine by directing the wave toward the mine. The apparatus generates the acoustic wave having a frequency that is approximately equal to the natural frequency of a component of the mine such that the wave causes the component to resonate in a manner that is sufficient to disable the mine from detonating, or that is sufficient to cause the mine to detonate.

Abstract: A propulsion unit control system is provided for a boat having plural propulsion units provided side by side and electrically connected in association with two adjacent operation levers. The control system synchronizes engine speeds of the respective propulsion units with each other in light of inputs to the two operation levers. The control system computes a deviation between the averaged engine speed of a reference propulsion unit and the averaged engine speed of a propulsion unit to be synchronized, and corrects a throttle opening of the propulsion unit to be synchronized based on the computed deviation in order to synchronize the engine speeds of the respective propulsion units with each other.

Abstract: A trimmable rudder system for a marine vessel such as a planing power boat, the system including a pair of rudder assemblies, each of which includes a rudder blade movably coupled to the hull by way of a ball-and-socket joint. Each rudder assembly includes a rudder shaft that extends from the rudder blade through the ball-and-socket joint and can be rotated for rotating the rudder blade to steer the power boat. Each rudder shaft may be operably coupled to a pair of actuators configured to control trim and camber positions of the rudder blade so that the pair of rudder blades can collectively achieve a desired hull trim change, including listing control and planing control of the power boat. Steering position, trim position, and camber position of the rudder blades may be simultaneously changed.

Abstract: A steering system for boats includes a control member of the steering wheel type, lever type or the like connected to a driving shaft of a transmission composed of at least two transmission elements dynamically engaged one with the other, of which one is an input and the other one an output elements. The output element drives a member transferring the motion of the control member to an operating unit, such that a movement/rotation of the control member is transmitted to the transfer member through such transmission. Moreover, at least the input element is produced from a material obtained by a sintering process.

Abstract: A system for use with a balloon having a balloon envelope is provided. The system includes a tendon assembly for mounting tendons to the balloon envelope. This tendon assembly includes a plate structure having a fill port attached to an apex of the balloon envelope and a plurality of tendons arranged over the plate structure. The fill port is configured to allow lift gas to pass into balloon envelope. Each tendon of the plurality of tendons has a first portion, a second portion, and a middle portion disposed between the first portion and the second portion. The first portion of a given tendon is arranged to engage a first section of the plate structure. The second portion is arranged to engage a second section of the plate structure opposite of the first section. The middle portion is arranged to wrap around the fill port of the plate.

Abstract: An aerodynamic blunt aft body (10) of a helicopter fuselage with two strakes (7, 8) along an aft surface (9) and/or respective left hand and right hand side fuselage surfaces (5, 6). Each strake (7, 8) is defined by first and second intersection lines (3, 4) resulting from intersections of horizontal planes (z) with the surface of the aft surface (9) or the respective left hand and right hand side fuselage surfaces (7, 8). The strakes are defined by a two or three dimensional spline (12) from the surface (2) towards the aft surface (9) inside said first and second intersection lines (3, 4) and inside the bounding box (15).

Abstract: Systems, devices, and methods for a transformable aerial vehicle are provided. In one aspect, a transformable aerial vehicle includes: a central body and at least two transformable frames assemblies respectively disposed on the central body, each of the at least two transformable frame assemblies having a proximal portion pivotally coupled to the central body and a distal portion; an actuation assembly mounted on the central body and configured to pivot the at least two frame assemblies to a plurality of different vertical angles relative to the central body; and a plurality of propulsion units mounted on the at least two transformable frame assemblies and operable to move the transformable aerial vehicle.

Abstract: A joint between a pair of aircraft components comprising a first component; a second component bonded to the first component over a bonded area, the bonded area terminating at an edge; a non-bonded area located between the edge of the bonded area and an edge of the second component, the components not being bonded over the non-bonded area; and one or more fasteners passing through the non-bonded area and fastening the first component to the second component.

Abstract: Device intended for a double glazing including at least one outer glazing and one inner glazing separated by an intermediary space filled with a gas, used to isolate an inside environment from an outside environment, a pressure variation being liable to occur between these environments, for example in the case of an aircraft in flight, includes means for conserving the outer glazing and the inner glazing of this double glazing mainly parallel, independently of this pressure variation. The invention also concerns a double glazing including this device, the process for maintaining parallelism and software using the process.

Abstract: A multilayer laminate comprising a first polymeric film layer capable of withstanding a temperature of at least 200 C for at least 10 min, a first adhesive layer having an areal weight of from 2 to 40 gsm capable of activation at a temperature of from 75 to 200 degrees C., an inorganic refractory layer comprising platelets in an amount of at least 85% by weight with a dry areal weight of 15 to 50 gsm and having a residual moisture content of no greater than 10 percent by weight, a second adhesive layer having an areal weight of from 4 to 40 gsm capable of activation at a temperature of from 75 to 200 degrees C. and a second polymeric film layer capable of withstanding a temperature of at least 200 C for at least 10 minutes.

Abstract: A seal assembly for closing an aperture in an aerodynamic surface of a structure, the seal assembly comprising: a track for attachment to the structure; and a retractable seal including a flexible substrate and a plurality of rods connected to the substrate, wherein at least one of the rods is mounted for running movement along the track, and the seal is moveable between an extended position and a retracted position by moving the at least one rod along the track accompanied by folding/unfolding of the seal substrate, and wherein the seal is biased to its extended position.

Abstract: A wing of an aircraft or spacecraft, the wing including at least a movable flow body, the wing including a movable support member, which is connected to the flow body, for rotating the flow body on the wing, the wing including a flow body control element, the flow body control element being fixed to the wing in a first point and the support member in a second point, the two points of the flow body control element and of the support member forming an axis, the flow body control element being formed at a predetermined angle to the axis and the flow body control element guiding the flow body in a predetermined plane about this axis.

Abstract: A slat cove filler is utilized to reduce airframe noise resulting from deployment of a leading edge slat of an aircraft wing. The slat cove filler is preferably made of a super elastic shape memory alloy, and the slat cove filler shifts between stowed and deployed shapes as the slat is deployed. The slat cove filler may be configured such that a separate powered actuator is not required to change the shape of the slat cove filler from its deployed shape to its stowed shape and vice-versa. The outer contour of the slat cove filler preferably follows a profile designed to maintain accelerating flow in the gap between the slat cove filler and wing leading edge to provide for noise reduction.

Abstract: An aircraft propulsion system has a propulsive rotor assembly rotatable about an axis of rotation and comprising a plurality of blades and a rotationally fixed vane assembly located adjacent to the propulsive rotor assembly and arranged circumferentially around the axis of rotation. As airflow enters the propulsive rotor assembly, a portion of the airflow passes over the vane assembly which is configured to direct the airflow away from the rotor blades so as to reduce the relative velocity of the redirected airflow over the rotor blades. This results in a reduced tendency of the airflow through the propulsive rotor assembly to become choked.

Abstract: The invention relates to a joystick (200) for controlling an aircraft, including a frame (201), a lever (202) mounted so as to be rotatably movable relative to the frame, and a mechanical linking assembly (203) for connecting the lever to the frame, the mechanical linking assembly (203) including: a first linking piece (213, 223) movably mounted relative to the frame (201) about a first rotation axis (X), a second linking piece (233, 243) movably mounted relative to the frame (201) about a second rotation axis (Y), the second rotation axis forming a non-zero angle with the first rotation axis, a third intermediate piece (255, 265) mounted so as to the rotatably movable relative to the first linking piece (213, 223) about a third rotation axis (Y?), a fourth intermediate piece (275, 285) mounted so as to be rotatably movable relative to the second linking piece (233, 243) about a fourth rotation axis (X?), the fourth rotation axis forming a non-zero angle with the third rotation axis, in which the linking piec

Abstract: A method of dynamically alleviating loads generated on an aircraft by a disturbance of gust and/or turbulence. The method comprises monitoring, during flight of the aircraft, to automatically detect a disturbance due to gust and/or turbulence and determining an incidence angle or angle of attack of the disturbance. When a disturbance due to gust and/or turbulence is detected, automatically generating control commands for deflecting control surfaces dependent on the incidence angle or angle of attack, and applying the control commands to deflect the control surfaces.

Abstract: Systems and methods are disclosed for selecting an emergency descent rate for an aircraft based on the rate of depressurization in the cabin of the aircraft. In one embodiment, the method includes the steps of detecting a depressurization warning for the cabin of the aircraft, and determining a rate of depressurization inside the cabin. The method further includes selecting a rate for an emergency descent for the aircraft in response to the depressurization warning based on the rate of depressurization inside the cabin, and initiating the emergency descent at the selected rate.

Abstract: A method for powering an autonomous drive device (4) in an aircraft comprising a certain number of drive motors (5) for the wheels (6) when the jet engines of the aircraft are not activated, the aircraft comprising an auxiliary power unit or APU (2) driving a first generator (1) for supplying power to devices on the aircraft that need to be powered when the jet engines are not activated. The method comprises the use of a second generator (8) dedicated to the power supply of the autonomous drive device, the second generator being disposed in parallel with the first generator so as to be driven by the APU and, when it operates as a motor under the action of power recovered by the autonomous drive device, so as to help the APU drive at least the first generator.

Abstract: Embodiments of the inventive concepts disclosed herein may provide visual and audible flight direction cues to the pilot of a helicopter to maintain an optimum energy sustaining profile to successfully perform an autorotation maneuver. From the moment the engine fails or fails to provide adequate power to the main rotor system, systems described herein provide airspeed, attitude, and altitude guidance to the pilot to intercept and fly the correct path for a successful autorotation entry and autorotation descent. The system displays specific cues as the helicopter approaches the determined flare altitude and guides the pilot through the autorotation flare and minimum rate of descent touchdown.

Abstract: Methods and systems for a full-scale vertical takeoff and landing manned or unmanned electric aircraft, having an all-electric, non-hydrocarbon-powered lift and propulsion system, an integrated avionics system for navigation and guidance, and simple joystick and throttle controls to provide the operator with ‘drive by wire’ style direction control. The vehicle employs counter-rotating sets of propellers and lift is provided by multiple pairs of small electric motors driving directly-connected, counter-rotating sets of propellers. Automatic computer monitoring by one or a plurality of programmed redundant digital motor management computer or autopilot controls each motor-controller and motor to produce pitch, bank and elevation, while simultaneously restricting the flight regime that the pilot can command. Sensed multi-axis information and parameter values about vehicle state are used to provide stable vehicle control and to detect when stable vehicle operating limits are about to be exceeded.

Abstract: Systems, devices, and methods for a transformable aerial vehicle are provided. In one aspect, a transformable aerial vehicle includes: a central body and at least two transformable frames assemblies respectively disposed on the central body, each of the at least two transformable frame assemblies having a proximal portion pivotally coupled to the central body and a distal portion; an actuation assembly mounted on the central body and configured to pivot the at least two frame assemblies to a plurality of different vertical angles relative to the central body; and a plurality of propulsion units mounted on the at least two transformable frame assemblies and operable to move the transformable aerial vehicle.

Abstract: An aircraft cargo handling system has a pair of load restraining rail assemblies, each of which has a shaft assembly running substantially parallel to the longitudinal axis of the aircraft. The shaft assembly has a plurality of lock pawls, each of which comprises a body having a cylindrical pallet-engaging surface. The pallet engaging surfaces of the lock pawls have increasing included angles at stations moving toward the front of the aircraft (or vice versa). This enables the pallets to be locked in place sequentially by rotating the shall assembly a predetermined angular rotation each time a pallet is loaded. Unloading of the aircraft is carried out in the reverse order, by rotating the shaft assembly in the opposite direction in steps to unlock each pallet individually as the aircraft is unloaded.

Abstract: A housing-free hatrack for a passenger cabin of an aircraft includes a hatrack body, at least one fixing brace and a support which is arranged between the hatrack body and one end of the fixing brace in such a way that the hatrack body is pivotable about a pivot axis. The other end of the fixing brace may be connected to a frame of an aircraft structure of the aircraft. This hatrack dispenses with the double-walled construction of conventional hatracks and the hatrack is therefore directly fixed to the structure of the aircraft.

Abstract: The invention relates to an independent refrigerator unit for an inflight service cart. According to the invention, it comprises an insulated casing part, inside which is a refrigerant chamber for a refrigerant, and a thermal conductor connected to the insulated casing, in which there is a first part and a second part, in which case the first part is in direct thermal contact with the refrigerant chamber and the second part with the external space of the casing.

Abstract: A tray table with an articulating support for portable electronic devices provides adjustable support for use of a portable electronic device at passenger seats of various forms of transportation, regardless of whether the tray table is in a stowed or service position. The articulating support comprises a plurality of rotating joints and rotating sections which combine to provide a plurality of refracted and extended positions, allowing a passenger to position his or her portable electronic device as desired. The articulating support secures the portable electronic device to prevent unwanted movement of the same, while also preserving unobstructed use of the top surface of the tray table when desired.

Abstract: A device for distributing air in a cargo aircraft includes using an air distribution system which is connected to a cargo deck. The air distribution system includes a source for bleed air, at least one air conditioning unit for treating the bleed air, a mixing unit which receives an air supply of recirculation air exiting the cargo deck and treated bleed air from the air conditioning unit, and at least one shut-off valve between the mixing unit and the cargo deck in order to interrupt or completely release the air supply to the cargo deck. A control unit establishes a desired air volume balance for the current operating state of the air distribution system and adjusts the flow volume through the at least one air conditioning unit such that the pressure prevailing in the mixing unit remains at a constant, predetermined value for all operating states.

Abstract: A method is provided that includes a number of operations performed in real-time during flight of the aircraft. That is, the method may include monitoring a continuous electrical signal output by a sensor on a surface of the aircraft, where a magnitude of the electrical signal may be related to an amount of ice buildup. The method may include calculating a liquid water content (LWC) value as a function of a rate of change of the electrical signal, and iteratively calculating a total water exposure (TWE) value as a function of the LWC value. The TWE value may represent a total water exposure of the aircraft from a time of an initial event, and may be calculated as a running total over a plurality of iterations. And the method may include performing a remedial or alert action in an instance in which the TWE value reaches a TWE threshold.

Abstract: A parachute canopy release comprising a harness strap and a parachute riser. The parachute riser has a terminal end connected to a riser ring. The harness strap has a connector assembly comprising a ring assembly and a latch assembly. The ring assembly has a middle ring and a small ring secured to the harness strap at middle and small ring securing straps, respectively. The latch assembly has a base and a latch slide engaging the base. The middle ring is inserted through an inner diameter of the riser ring, the small ring is inserted through an inner diameter of the middle ring, and the latch slide is manipulated such that the small ring is retained intermediate said base and an interior surface of said latch slide when said parachute riser is releasably connected to said harness strap.

Abstract: Described are airbag modules for a passenger door having a door bustle, an airbag positioned adjacent the door bustle, and an inflator positioned adjacent the door bustle. As examples, a pneumatic system is coupled to the inflator and the airbag, wherein the pneumatic system includes a slide lock that is configured to couple a girt bar of an escape slide to a passenger door sill when the inflator is activated. As additional examples, a valve is coupled to an inlet of the airbag, wherein the valve is configured to prevent the pressurized gas from flowing from the inflator to the airbag when the valve is closed and is configured to allow the pressurized gas to flow from the inflator to the airbag when the valve is open.

Abstract: A safe, quiet, easy to control, efficient, and compact aircraft configuration is enabled through the combination of multiple vertical lift rotors, tandem wings, and forward thrust propellers. The vertical lift rotors, in combination with a front and rear wing, permits a balancing of the center of lift with the center of gravity for both vertical and horizontal flight. This wing and multiple rotor system has the ability to tolerate a relatively large variation of the payload weight for hover, transition, or cruise flight while also providing vertical thrust redundancy. The propulsion system uses multiple lift rotors and forward thrust propellers of a small enough size to be shielded from potential blade strike and provide increased perceived and real safety to the passengers. Using multiple independent rotors provides redundancy and the elimination of single point failure modes that can make the vehicle non-operable in flight.

Abstract: Methods to monitor components of an aircraft landing system are disclosed herein. An example method includes determining a brake assembly temperature and determining a wheel temperature. The example method also includes retrieving an estimated increase in the wheel temperature from a data structure based on the wheel temperature and the brake assembly temperature. The example method further includes determining a maximum wheel temperature based on the wheel temperature and the estimated increase in the wheel temperature.